# TCDS 6A5: Lockheed Martin Aeronautics Company - Type: Type certificate data sheet - Status: Current - Holder: Lockheed Martin Aeronautics Company - Revision: 25 - Revised: July 23, 2012 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/f5/d9/f5d9daa1d42dbecf5efa39c46bd22df95c6fd28558f3f33c28121b88fea602d6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/562D52ACF2B2813186257A450049AA55.0001 - Page: https://openairdocs.org/tcds/6A5 ## Models (8) As the data sheet lists them. - 1049G-82 - 1049C-55 - 1049E-55 - 1049F-55 (USAF C-121C) - 1049D-55 - 1049B-55 (Navy R7V-1) - 1049H-82 - 1049-54 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 25 - - - - - - - 24 - - - - - - Page No. 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 Rev. No. - 24 - - - - - - - - - - - - - 24 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION 6A5 Revision 25 LOCKHEED 1049-54 1049B-55 (Navy R7V-1) 1049C-55 1049D-55 1049E-55 1049F-55 (USAF C-121C) 1049G-82 1049H-82 July 23, 2012 AIRCRAFT SPECIFICATION NO. 6A5 This data sheet which is part of Type Certificate No. 6A5 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Lockh eed Martin Aeronautics Company 86 South Cobb Drive Marietta, GA 30063 Type Certificate Holder Record Lockheed Aircraft Corporation Burbank, California I - Model 1049-53 deleted June 9, 1953. All 1049-53 aircraft converted to Model 1049-54. II - Model 1049-54, Approved May 14, 1952 Engines 4 Wright Cy clones 975C18CB-1 with 16:7 reduction gear ratio Fuel AN grade 115/145 (See NOTE 15 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 48.0 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressu re variation with altitude to 5300 ft.) 46.0 in. hg., 2600 rpm (2400 hp) Take-off (2 minutes): (Sea level) 54.5 in.hg., 2900 rpm (2800 hp) (Straight line manifold pressu re variation with altitude to 4500 ft.) 52.5 in.hg., 2900 rpm (2800 hp). High impeller ratio 8.67:1 Maximum continuous: (10,800 ft.) 47.5 in.hg., 2600 rpm (2000 hp) (Straight line manifold pressure variation with altitude to 16,000 ft.) 46.0 in.hg., 2600 rpm (2000 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 11,000' reduce speed 10 mph ( 9 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 11,000' reduce speed 12 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 208 mph (180 knots) True Ind. Vf (Takeoff position-60%) 212 mph (184 knots) True Ind. 6A5 2 Vf (Approach position-66%) 186 mph (161 knots) True Ind. Vf (80%) 177 mph (153 knots) True Ind. Vf (Landing position-100%) 171 mph (148 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .54 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft. Limit lbs. gear sta. %MAC sta. %Mac Take-off 120,000* Down 665.8* 21.0 685.2 32.0 98,500* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 98,500 Down 660.5 18.0 685.2 32.0 o r l e s s Cruising 120,000* Up 661.5* 18.6 688.7 34.0 Flight 98,500* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. Weight limits Landing 98,500 lb s. See NOTE 8 for higher weight (See NOTE 15 for Take-off 120,000 lbs. (Dump valves are required) limits when using Maximum zero fuel weight 93,500 lbs. S ee NOTES 1(e) for fuel loading and 8 for low grade fuel) higher weight. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Copilot at +190 and Flight Engineer at +226. Passengers Maximum 88 (CAR 4b.433). See Appr oved Weight and Balance Report for actual number and location. Baggage Maximum capacity of internal baggage and storage compartments: Vol. Max. Floor Cap. Compt. (cu. ft.) loading psf (lbs. ) C.G. Fwd. cargo compartment, fwd. portion F.S. 333.6 to 482 72 70 1440 (+407.8) Fwd. cargo compartment, aft portion F.S. 482 to 638 194 70 3880 (+560) Aft cargo compartment, fwd. portion F.S. 750 to 932 230 70 4600 (+841) Aft cargo compartment, aft portion F.S. 932 to 1139.8 160 70 3200 (+1036) -67 interior Left hand fwd. 450 (+ 497) Right hand fwd. 700 (+ 497) Left hand aft 600 (+1150) Wash water, -67 interiors 209 (+1075) Galley water, -67 interiors 125 (+ 380) Galley installation and supplie s, 67 interiors 45 (a) (a) Galley areas between Stations 260 a nd 343.5 are structurally satisfactory for a uniformly distributed load over the en tire area of 45 psf or a uniformly distributed load of 55 psf on each side of the 20 inch aisle. Galley installations and their contents shall not exceed these loadings. Fixed equipment such as galleys shall be listed on the Approved Equipment List together with pertinent weights and arms. Fuel capacity See NOTE 1(c) regard ing "Usable fuel and System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692) Tanks 1 and 4 (middl e) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687) Tank 5 (center section ( 730 gallons ) 4,380 lbs. (+694) when installed) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel and System Oil." 3 6A5 (a) (2 inboard tanks (with aux. tank) and (58 gal.ea.) 870 lbs. (+584) (2 outboard tanks (with aux. tank); or (58 gal.ea.) 870 lbs. (+603). (b) (2 inboard tanks (without aux. tank) and (55 gal.ea.) 825 lbs. (+584) (2 outboard tanks (without aux. tank) (55 gal.ea.) 825 lbs. (+603). Serial Nos. eligible 1049/4001 th rough 1049/4024 (See Equipment Item 400) Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(a) or (c); 101(a) or (b); 103(a ); 104(a); 105(a); 107(a) or (b); 200(a) or (b); 201(a); 202(a)(1), (2) or (3); 203(a) or (b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(a) or (b); 300(a); 301(a); 303(a) or (b); 400; 440; 441(a) or (b); 508(a). III - Model 1049B-55 (Navy R7V-1), Approved October 28, 1953. (Same as Model 1049-54 except engines, design weights, and certain structural changes. This airplane is basically a cargo rather than passenger carrier) (See NOTE 5 for modifications necessary for civil conversion of R7V-1). Engines 4 Wright Cyclones 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive r a t i o . Fuel AN grade 115/145 (See NOTE 16 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure vari ation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp) (Straight line manifold pressure vari ation with altitude to 5000 ft.) 53.0 in.hg., 2900 rpm (3250 hp). High impeller ratio 8.67:1 Maximum continuous: (9,550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for ea. additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for ea. additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft. Limit lbs. gear sta. %MAC sta. %Mac Take-off 135,000* Down 667.2* 21.0 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6 18.0 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. 6A5 4 Weight limits Landing 110,000 lbs. (See NOTE 16 for Takeoff 133,000 lbs. # with auto-feathe ring (Dump valves are required.) See limits when using Equipment Item 1 (b), or (c) or (d) for takeoff weight low grade fuel) with auto feathering inoperative. #130,000 lbs. for serial No s. 4101 through 4139 unless modified in accordance with NOTE 6. Maximum zero fuel weight 105,000 lb s. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Co-pilot at +190 and Flight Engineer at +226. Passengers All Serial Numbers originally cer tificated as cargo carriers. See NOTE 9 for conversion to pa ssenger configuration. Maximum cargo Maximum Maximum Floor Compartment Station Cap. (lbs.) loading psf Arm C (Main Cabin) 260-287 1000** 300 274 D (Main Cabin) 287-370 3900 300 329 E (Main Cabin) 370-444 6100 300 408 F (Main Cabin) 444-509 5400 300 477 G (Main Cabin) 509-583 6100 300 546 H (Main Cabin) 583-656 6100 300 620 I (Main Cabin) 656-732 6300 300 694 J (Main Cabin) 732-806 6100 300 769 K (Main Cabin) 806-879 6100 300 842 L (Main Cabin) 879-953 6100 300 916 M (Main Cabin) 953-1026 6100 300 989 N (Main Cabin) 1026-1158 7200 300 1089 O (Main Cabin) 1158-1258 2900 300 1198 Q (Lower Cargo Compt) 334-482 2800 70 402 R (Lower Cargo Compt) 482-638 5040 70 558 S (Lower Cargo Compt) 750-932 5950 70 821 T (Lower Cargo Compt) 932-1140 6370 70 1004 Maximum combined accumu lated load of both cabin and lower cargo compartments from extremities of cabin toward main frames: Forebody Afterbody From Sta. 260 to From Sta. 1258 forward to: Sta. 287 300 lbs. Sta. 1158 2,900 lbs. Sta. 370 3,900 lbs. Sta. 1026 7,200 lbs. Sta. 444 6,900 lbs. Sta. 953 9,800 lbs. Sta. 509 9,700 lbs. Sta. 879 14,100 lbs. Sta. 583 14,700 lbs. Sta. 806 18,300 lbs. Sta. 656 20,800 lbs. Sta. 732 23,500 lbs. ** Including radio and galley equipment (700#) in compartment C. All cargo loading must be secured with the tie-downs provided since there are no restraining or crash bulkhead provisions. Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692). Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687). Tank 5 (center section) ( 730 gallons) 4,380 lbs. (+694) 5 6A5 Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel & System Oil." 2 inboard tanks (40 gal. ea.) 600 lbs. (+634) 2 outboard tanks (40 gal. ea.) 600 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049B/4101 through 1049B/4111; 1049B/4122 through 1049B/4130; 1049B/4133 through 1049B/4150; 1049B/4152 through 1049B/4160; and 1049B/4167 through 1049B/4169. Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (c) or (d); 101(c), (d), (e), (f), (g) or (h); 103(b) or (c); 104(b) or (c); 105(a); 107(b); 200(b); 201(a); 202(a)(2) or (3); 203(b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(a) or (b); 300(b); 301(a); 303(c) or (e); 400; 440; 441(e); 508(a). IV - Model 1049C-55, Approved June 9, 1953, and Model 1049E-55, Approved May 26, 1954. (Same as Model 1049-54 except engines, design weights, structural changes of wings, fuselage, nacelles and landing gear, and installation of sealed "Class D" lower cargo compartments. The Model 1049E-55 is the same as the Model 1049C-55 with miscellaneous structural revisions.) Engines 4 Wright Compound 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive ratio. (Also eligible with 972TC18DA3, 988TC18EA3, and 988TC18EA6. See Item 111 for engine limits with these engines) Fuel AN grade 115/145 (See NOTE 16 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure va riation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes at sea level; 5 minutes at 7500 ft.; straight line variation of takeoff power time with altitude to 7500 ft.): (Sea level) 56.5 in.Hg., 2900 rpm (3250 hp) (Straight line manifold pressure vari ation with altitude to 5000 ft.) 53.0 in.Hg., 2900 rpm (3250 hp) High impeller ratio 8.67:1 Maximum continuous: (9550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 6A5 6 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 670.3* 23.5 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 664.9 20.5 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. Weight limits Landing 110,000 lbs. S ee NOTE 13 for higher landing weight. (See NOTE 16 for Takeoff 133,000 lbs. with autofeat hering (Dump valves are required. limits when using See Equipment Item 1(b), (c), (d), (e) or (f) low grade fuel.) for takeoff weight with autofeathering inoperative, and NOTE 7 for takeoff weight when oil transfer system is not installed. See NOTE 12 for higher takeoff weight. Maximum zero fuel weight 103,500 lb s. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Co-pilot at +190 and Flight engineer at +226. Passengers Maximum 99 occupant s (passengers plus crew) (CAR 4b.433 and SR 389 effective October 27, 1952.) See Approved Wei ght and Balance Report for actual number and location. Baggage Maximum capacity of intern al baggage and storage compartments: Vol. Max. Floor Cap. Compt. (cu. ft.) loading psf (lbs. ) C.G. (A) Fwd. cargo compartment, fwd. portion F.S. 334 to 482 77 70 1500 (+402) (B) Fwd. cargo compartment, aft portion F.S. 482 to 638 194 70 3880 (+558) (C) Aft cargo compartment, fwd. portion F.S. 750 to 932 230 70 4600 (+821) (D) Aft cargo compartment, aft portion F.S. 932 to 1140 194 70 3880 (+1004) Coat closet 200 (+1000) Coat closets L. & R. 400 (+1165) Wash water 500 (+ 980) Galley areas between Stations 930 and 1014 and 10" from airplane centerline R.H. side is structurally satisfactory for a maximum total load of 2,300 pounds, with a maximum unit floor loading of 70 pounds per square foot. Galley storage area between Stations 930 and 950 and 10" from airplane centerline L.H. side is structurally satisfactory for a maximum total load of 500 pounds with a maximum unit floor loading of 90 pounds per square foot. Cabin Cargo Compartment A (optiona l) Fus. Sta. 260-339 R.H. 900 (+309) Cabin Cargo Compartment B ( optional) Fus. Sta. 339-467.5 5200* (+403) *With lower cargo Compartment A empty. Maximu m capacity must be decreased by the amount of any load carried in lo wer cargo Compartment A. 7 6A5 Fuel capacity See NOTE 1(c) regard ing "Usable fuel and System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692) Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687) Tank 5 (center section) ( 730 gal. ea.) 4,380 lbs. (+694) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel and System Oil." 2 inboard tanks (40 gal. ea.) 600 lbs. (+634) 2 outboard tanks (40 gal. ea.) 600 lbs. (+636). 1 auxiliary cell (center sect.) (67 gal. ea.) 502 lbs. (+674) Serial Nos. eligible 1049C/4501 through 1049C/4548; 1049E/4549 through 1049E/4665, 1049E/4573, 1049E/4574; 1049E/4578 through 1049E/4581; 1049E/4606, 1049E/4607; 1049E/4613 through 1049E/4615. Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (c), (d), (e) or (f); 101(c), (d ), (e), (f), (g) or (h); 103(b) or (c); 104(b) or (c); 105(a); 107(b); 200(b); 201(a); 202(a)(2 ) or (3); 203(b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(a) or (b); 300(b); 301( a); 303(c) or (e); 400; 440; 441(c), (d) or (f); 508(a). V - Model 1049D-55, Approved August 12, 1954. (Same as Model 1049B-55 except for passenger seat installation, additional emergency exits are installed, and the lower cargo compartments are Class D per CAR 4b-383(d).) Engines 4 Wright Compound 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive ratio. (Also eligible with 972TC18DA3, 988TC18EA3 and 988TC18EA6. See Item 111 for engine limits with these engines) Fuel AN grade 115/145 (See NOTE 16 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure va riation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes at sea level; 5 minutes at 7500 ft.; straight line variation of ta keoff power time with altitude to 7500 ft.): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp) (Straight line manifold pressure va riation with altitude to 5000 ft.) 53.0 in.hg., 2900 rpm (3250 hp). High impeller ratio 8.67:1 Maximum continuous: (9550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressu re variation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 6A5 8 C.G. range See NOTE 1(b) for required loading and gear retraction moment. (A) Passenger or Mi xed Cargo-Passenger Loading Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 670.23* 23.5 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6* 20.5 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s *Straight line variation between these values. (B) All Cargo Loading Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 670.23* 21.8 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6* 18.6 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s *Straight line variation between these values. Weight limits Landing 110,000 lbs. (See NOTE 11 for Takeoff 133,000 lbs. with autofeat hering (Dump valves are required. higher weights; See Equipment Item 1(b), (c), (d), (e) or (f) NOTE 16 for weight for takeoff weight with autofeathering inoperative, limits when using low and NOTE 7 for takeoff weight when oil transfer grade fuel; NOTE 19 system is not installed. Maximum zero fuel weight for application of SR-411A) 105,000 lbs. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew passengers 3. Pilot and Copilot at +190 and Flight Engineer at +226. Maximum 112 occupants (passengers plus crew) (CAR 4b. 433 and SR 389 effective October 27, 1952.) See approved Weight and Balan ce Report for actual number and location. 9 6A5 Maximum cargo Ma ximum Maximum Floor Compartment Station Cap. (lbs.) loading psf Arm A (Main Cabin) 260-339 2900 300 300 B (Main Cabin) 339-444 7200 300 392 C (Main Cabin) 444-509 5400 300 477 D (Main Cabin) 509-583 6100 300 546 E (Main Cabin) 583-656 6100 300 620 F (Main Cabin) 656-732 6300 300 694 G (Main Cabin) 732-806 6100 300 769 H (Main Cabin) 806-879 6100 300 842 I (Main Cabin) 879-953 6100 300 916 J (Main Cabin) 953-1026 6100 300 989 K (Main Cabin) 1026-1158 7700 300 1089 L (Main Cabin) 1158-1258 3400 300 1198 A (Lower Cargo Compt) 334-482 2800 70 402 B (Lower Cargo Compt) 482-638 5040 70 558 C (Lower Cargo Compt) 750-932 5950 70 821 D (Lower Cargo Compt) 932-1140 6370 70 1004 Maximum combined accu mulated load of both cabin and lower cargocompartments from extremities of cabin toward main frames: Forebody Afterbody From Sta. 260 to: From Sta. 1258 forward to: Sta. 339 2,900 lbs. Sta. 1158 3,400 lbs. Sta. 444 7,200 lbs. Sta. 1026 7,700 lbs. Sta. 509 10,000 lbs. Sta. 953 10,300 lbs. Sta. 583 15,000 lbs. Sta. 879 14,600 lbs. Sta. 656 21,100 lbs. Sta. 806 18,800 lbs. Sta. 732 24,000 lbs. All cargo loading must be secured with the tie-downs provided since there are no restraining or crash bulkhead provisions. Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692). Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687). Tank 5 (center section) ( 730 gallons) 4,380 lbs. (+694) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel & System Oil." 2 inboard tanks (40 gal. ea.) 600 lbs. (+634) 2 outboard tanks (40 gal. ea.) 600 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049D/4163 through 1049D/4166 Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (c), (d), (e) or (f); 101(c), (d ), (e), (f), (g) or (h); 103(b) or (c); 104(b) or (c); 105(a); 107(b); 200(b); 201(a); 202(a)(2 ) or (3); 203(b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(b); 300(b); 301(a); 303(c) or (e); 400; 440; 441(g); 508(a). VI - Model 1049G-82, Approved January 14, 1955. (Same as Model 1049C except engines, propellers, brakes, provisions for tip tanks and structural reinforcements.) Engines 4 Wright Compound 972TC18DA3 with 16:7 reduction gear ratio and 6.52:1 turbo drive ratio. (Also elig. with 988TC 18EA3 & 988TC18EA6. See Item 111 for engine limits with these engines.). Fuel AN grade 115/145. (See NOTE 17 for engine limits when using low grade fuel) 6A5 10 Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 49.0 in.hg., 2600 rpm (2700 hp) (Straight line manifold pressure vari ation with altitude to 5800 ft.) 47.0 in. hg., 2600 rpm (2750 hp) Takeoff (2 minutes at sea level; 5 minutes at 7500 ft.; straight line variation of ta keoff power time with altitude to 7500 ft.): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp). (Straight line manifold pre ssure variation with altitude to 5500 ft.) 53.5 in.Hg., 2900 rpm (3250 hp) High impeller ratio 8.67:1 Maximum continuous: (10,050 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (261 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (294 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va Maneuvering) 222 mph (193 knots) True Ind. Vf Takeoff position-60%) 224 mph (195 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 182 mph (158 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 137,500* Down 671.3* 24.1 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 113,000* Down 665.8 21.0 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 137,500* Up 667.0* 21.7 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. Weight limits Landing 113,000 lbs. (See NOTE 17 for Takeoff 137,500 lbs. with autofeathering (Dump valves are weights using low required). See Equipment Item 1(b), (e) or (f) for takeoff weight with autofeathering grade fuel) autofeathering inoperative. Maximum zero fuel weight 103,500 lbs. (tip tanks off) 104,200 lbs. (tip tanks on) See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Co-pilot at +190 and Flight Engineer at +226. Passengers Maximum 112, 104 or 96 occupants (passengers plus crew) with 11, 10 or 9 usable passenger exits, respectively. (CAR 4b.433 and SR 389 effective October 27, 1952.) See approved Weight and Balan ce Report for actual number and location. 11 6A5 Baggage Maximum capacity of intern al baggage and storage compartments: Vol. Max. Floor Cap. Compt. (cu. ft.) loading psf (lbs. ) C.G. (A) Fwd. cargo compartment, fwd. portion F.S. 334 to 482 75 70 1500 (+402) (B) Fwd. cargo compartment, aft portion F.S. 482 to 638 194 70 3880 (+558) (C) Aft cargo compartment, fwd. portion F.S. 750 to 932 230 70 4600 (+821) (D) Aft cargo compartment, aft portion F.S. 932 to 1140 194 70 3880 (+1004) Coat closet 200 (+1000) Coat closets L. & R. 400 (+1165) Wash water 500 (+ 980) Galley areas between Stations 930 and 1014 and 10" from airplane centerline R.H. side is structurally satisfactory for a maximum total load of 2,300 pounds, with a maximum unit floor loading of 70 pounds per square foot. Galley storage area between Stations 930 and 950 and 10" from airplane centerline L.H. side is structurally satisfactory for a maximum total load of 500 pounds with a maximum unit floor loading of 90 pounds per square foot. Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) (790 gal. ea.) 9480 lbs. (+692). Tanks 1 and 4 (middle) (1555 gal. ea.) 18660 lbs. (+689) Tanks 2a and 3a (outboard ) (565 gal. ea.) 6780 lbs. (+687). Tank 5 (center section) (730 gallons) 4380 lbs. (+694) Tanks 1a and 4a (wing tips) (609 gal. ea.) 7308 lbs. (+688) Oil capacity See NOTE 1(c) regarding "Unusable Fuel and Oil System Oil." 2 inboard tanks (42.5 gal. ea.) 638 lbs. (+634) 2 outboard tanks (42.5 gal. ea.) 638 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049G/4572, 1049G/ 4575 through 1049G/4577, 1049G/4582 through 1049G/4605; 1049G/4608 through 1049G/4612, 1049G/4616 through 1049G/4699. Required equipment In addition to the per tinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (e) or (f); 101(i), (j), (k), or (l); 103(b) or (c); 104(b), (c), or (d); 105(a); 107(b); 200(d); 201(a); 202(a)(3) or (a)(4); 203(b); 204(a)(1), (a)(2), (a)(3) or (b)(1); 205(a) or (b); 206(c); 300(b) or (c); 301(a); 303(c), (d) or (e); 400; 440; 441(h) or (i); 508(c) or (d). VII - Model 1049F-55 (USAF C121C), Approved October 10, 1955. (Same as Model 1049B-55 except 34 rectangular windows replace 17 round windows, Class D lower cargo compartments replace Class C compartments, Solar APU replaces AiResearch APU, and heater is added to nose radome. This airplane is basically a cargo rather than a passenger carrier). (See NOTE 5 for modifications necessary for civil conversion of C121C). Engines 4 Wright Compound 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive ratio. Fuel Grade 115/145 (See NOTE 16 for engi ne limits when using low grade fuel) 6A5 12 Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure variation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes at sea level; 5 minutes at 7500 ft.; straight line varia tion of takeoff power time to 7500 ft.): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp) (Straight line manifold pressure variation with altitude to 5000 ft.) 53.0 in.hg., 2900 rpm (3250 hp). High impeller ratio 8.67:1 Maximum continuous: (9550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 677.2* 21.1 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6 18.6 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 665.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. Weight limits Landing 110,000 lbs. (See NOTE 16 for Takeoff 133,000 lbs. with autofeat hering (Dump valves are required.) weights when using See Equipment Item 1(b), (e) or (f) for takeoff weight with autofeathering low grade fuel) inoperative. Maximum zero fuel weight 105,000 lb s. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Co-pilot at +190 and Flight Engineer at +226. Passengers All serial numbers origin ally certificated as cargo carriers. See Note 9 for conversi on to passenger configuration. 13 6A5 Maximum cargo Maximum Maximum Floor Compartment Station Cap. (lbs.) loading psf Arm C (Main Cabin) 260-287 1000** 300 274 D (Main Cabin) 287-420 5900 300 355 E (Main Cabin) 420-509 7400 300 465 F (Main Cabin) 509-583 6100 300 546 G (Main Cabin) 583-656 6100 300 620 H (Main Cabin) 656-732 6300 300 694 I (Main Cabin) 732-806 6100 300 769 J (Main Cabin) 806-879 6100 300 842 K (Main Cabin) 879-953 6100 300 916 L (Main Cabin) 953-1026 6100 300 989 M (Main Cabin) 1026-1158 7200 300 1089 N (Main Cabin) 1158-1258 2900 300 1198 P (Lower Cargo Compt) 334-482 2800 70 402 Q (Lower Cargo Compt) 482-638 5040 70 558 R (Lower Cargo Compt) 750-932 5950 70 821 S (Lower Cargo Compt) 932-1140 6370 70 1004 Maximum combined accu mulated load of both cabin and lower cargocompartments from extremities of cabin toward main frames: Forebody Afterbody From Sta. 260 to: From Sta. 1258 forward to: Sta. 287 300 lbs. Sta. 1158 2,900 lbs. Sta. 420 5,900 lbs. Sta. 1026 7,200 lbs. Sta. 509 9,700 lbs. Sta. 953 9,800 lbs. Sta. 583 14,700 lbs. Sta. 879 14,100 lbs. Sta. 656 20,800 lbs. Sta. 806 18,300 lbs. Sta. 732 23,500 lbs. **Including radio and galley equipment (700#) in compartment C. All cargo loading must be secured with the tie-downs provided since there are no restraining or crash bulkhead provisions. Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692) Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687) Tank 5 (center section) ( 730 gallons) 4,380 lbs. (+694) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel & System Oil." 2 inboard tanks (42.5 gal. ea.) 638 lbs. (+634) 2 outboard tanks (42.5 gal. ea.) 638 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049F/4170 through 1049F/4202. Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(c); 101(d); 103(b) or (c); 104(b), (c) or (d); 105(a) and (b); 107(b); 200(b), (c) or (d); 201(a); 202(a)(2), (a)(3) or (a)(4); 203(b ); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(b) or (d); 300(b); 301(a); 303(d) or (e); 400; 440; 441(j); 508(a) or (b). 6A5 14 VIII - Model 1049H-82, Approved October 9, 1956. (Same as Model 1049D/01-55, except for engines of higher power rating, higher takeoff weight; and other minor changes.) Engines 4 Wright Compound 972TC18DA3 with 16:7 reduction gear ratio and 6.52:1 turbo drive ratio. (Also eligible with 988TC18EA3 and 988TC18EA6. See Item 111 for engine limits with these engines.) Fuel Grade 115/145. (See NOTE 17 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 49.0 in.hg., 2600 rpm (2700 hp) (Straight line manifold pressure va riation with altitude to 5800 ft.) 47.0 in. hg., 2600 rpm (2750 hp) Take-off (2 minutes at sea level; 5 minutes at 7500 ft.; straight line variation of takeoff power time with altitude to 7500 ft.): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp). (Straight line manifold pressure variation with altitude to 5500 ft.) 53.5 in.Hg., 2900 rpm (3250 hp) High impeller ratio 8.67:1 Maximum continuous: (10,050 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (261 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (294 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 222 mph (193 knots) True Ind. Vf (Takeoff position-60%) 224 mph (195 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 182 mph (158 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 C.G. range See Note 1(b) for requi red loading and gear retraction moment. (A) Passenger or Mi xed Cargo-Passenger Loading Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 137,500* Down 671.3* 24.1 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 113,000* Down 665.8* 21.0 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 137,500* Up 667.0* 21.7 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s 15 6A5 (B) All Cargo Loading Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 137,500* Down 668.4* 22.4 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 113,000* Down 662.3* 19.0 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 137,000* Up 667.0* 21.7 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s *Straight line variation between these values. Weight limits Landing 113,000 lbs. S ee NOTE 14 for higher landing weight. (See NOTE 17 for Takeoff 137,500 lbs. with autofeat hering (Dump valves are required. limits when using See Equipment Item 1(b), (e) or (f) for takeoff low grade fuel, and weight with autof eathering inoperative, and Note 19 for and NOTE 14 for for higher takeoff weight. application of SR-411A) Maximum zero fuel weight 108,000 lbs. (tip tanks off) 104,200 lbs. *tip tanks on) See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew passengers 3. Pilot and Cop ilot at +190 and Flight Engineer at +226. Passengers Maximum 112 occupant s (passengers plus crew) (CAR 4b.433 and SR 389 effective October 27, 1952.) See approved Weight and Balance Report for actual number and location. Maximum cargo Ma ximum Maximum Floor Compartment Station Cap. (lbs.) loading psf Arm A (Main Cabin) 260-339 2900 300 300 B (Main Cabin) 339-444 7200 300 392 C (Main Cabin) 444-509 5400 300 477 D (Main Cabin) 509-583 6100 300 546 E (Main Cabin) 583-656 6100 300 620 F (Main Cabin) 656-732 6300 300 694 G (Main Cabin) 732-806 6100 300 769 H (Main Cabin) 806-879 6100 300 842 I (Main Cabin) 879-953 6100 300 916 J (Main Cabin) 953-1026 6100 300 989 K (Main Cabin) 1026-1158 7700 300 1089 L (Main Cabin) 1158-1258 3400 300 1198 A (Lower Cargo Compt) 334-482 2800 70 402 B (Lower Cargo Compt) 482-638 5040 70 558 C (Lower Cargo Compt) 750-932 5950 70 821 D (Lower Cargo Compt) 932-1140 6370 70 1004 Maximum combined accumu lated load of both cabin and lower cargo compartments from extremities of cabin toward main frames: Forebody Afterbody From Sta. 260 to: From Sta. 1258 forward to: Sta. 339 2,900 lbs. Sta. 1158 3,400 lbs. Sta. 444 7,200 lbs. Sta. 1026 7,700 lbs. Sta. 509 10,000 lbs. Sta. 953 10,300 lbs. Sta. 583 15,000 lbs. Sta. 879 14,600 lbs. Sta. 656 21,100 lbs. Sta. 806 18,800 lbs. Sta. 732 24,000 lbs. All cargo loading must be secured with the tie-downs provided since there are no restraining or crash bulkhead provisions. 6A5 16 Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692). Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687). Tank 5 (center section) ( 730 gallons) 4,380 lbs. (+694) Tanks 1a and 4a (wing tips) (609 gal. ea) 7,308 lbs. (+688) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel & System Oil." 2 inboard tanks (42.5 gal. ea.) 638 lbs. (+634) 2 outboard tanks (42.5 gal. ea.) 638 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049H/4801 through 1049H/4853 Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (e) or (f); 101(i), (j), (k), or (l); 103(b) or (c); 104(b), (c), or (d); 105(a); 107(b); 200(d); 201(a); 202(a )(3) or (a)(4); 203(b); 204(a)(1), (a)(2) (a)(3), or (b)(1); 205(a) or (b); 206(c); 300(b) or (c); 301(a); 303(c), (d) or (e); 400; 440; 441(g) or (k); 508(c) or (d). SPECIFICATIONS PERTINENT TO ALL MODELS Datum 730.2 in. forward of jig point. (Screw head on bottom surface of wing 1.8 in. fwd. of center line of rearbeam and 3.5 in inboard of wing sta. 80). MAC 176 inches. Leading edge of MAC Sta. 628.8. Leveling means Leveling plate under fuselage floor at ref. Sta. 657. Control surface movements Main surfaces ( booster pressure on) - Elevator 40° up 20° down Aileron 25° up 10° down Rudder 30° right 30° left Tabs (main surfaces in ne utral) - Elevator 22° up 22° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 41° total angular travel. Certification basis Type Ce rtificate No. 6A5 (CAR 4b - as amended to October 1, 1949.) All 1049 Series Models have been examined and found to comply with the Standards of Transport Category A of Annex 8 to th e Convention on International Civil Aviation, entitled "Airworthiness of Aircraft," as amended to December 1949 with the following exception: 1. 2.4.4 Stalling, Symmetrical Power. Compliance with the ditching require ments of CAR 4b has been demonstrated. Maximum approved ope rational altitude 25,000 ft. Production basis Producti on Certificate No. 600. Equipment: A plus (+) or minus (-) sign pr eceding the weight of an item of equipment indicates net weight change when that item is installed. Approval for the installation of all items of equi pment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the ai rcraft manufacturer. An item marked with an asterisk may not have been manufactured under a FAA monitored or approved quality control system, and therefore conformity must be determined if the item is not identified by a Fo rm FAA-186, PMA or other evidence of FAA production approval. Propellers and Propeller Accessories (Except De-Icing Equipment) 1a. (1) 4 Propellers - Ham. Std. hubs 43E60, blades 6901-02 2281 lb. (+509) (including sli ngers and shoes) Diameter: Max. 15' 1-5/16", min. allowable for repairs 14' 9-3/16". No further reduction permitted. Pitch settings at 72 in. sta.: Lo w fwd. 12°, low reverse -21.5°, propeller feathering setting must prevent engine windmilling (Approximately 81.5°) Propellers and 17 6A5 (2) 4 Propeller spinners - Ham. Std. 76832 80 lbs. (+509) (3) 4 Feathering pumps - Pesco 1E-777-ML-1 (Mod.) 58 lbs. (+604) (4) 4 Propeller governors Ham. Std. Type 5AA-22-8 or 5U18 (See NOTE 20) 56 lbs. (+531) (5) 4 Master Synchronizer Genera tors Kollsman 1135GH-0120304 17 lbs. (+578) (6) 1 Propeller Synchroni zing Control Box Ham. Std. Dwg. 322080 40 lbs. (+193) b. (1) 4 Propellers - Curtiss Electri c hubs C634S-S, blades 2586 lbs. (+509) 858-5C4-0 (includi ng slingers and shoes) with or without trailing edge extension. (G & H Series Models equipped with th is propeller must use trailing edge extension). Diameter 15'0". Pitch settings at 54 in. sta.: low fwd. 23.7° low reverse -11.8°, propeller feathering pitch setting must prevent engine windmilling (approximately 91.2°). Placard required in full view of flight engineer: "Do not operate propellers in flight below 1500 engine rpm." Max. takeoff wt. auto-f eathering inoperative - 129,800 lbs. (2) 4 spinners - Curtiss Type 145491 84 lbs. (+509) (3) 4 Alternators - Curtiss Type 124512 16 lbs. (+545) (4) 1 Synchronizer Master Unit - Curtiss Type 119778-20 40 lbs. (+195) (5) 2 Voltage boosters Curtiss Type 116285-231 40 lbs. (+252) (6) 1 Master Unit Filter Cu rtiss Type 112148-9 6 lbs. (+171) (7) 4 Nacelle Filters Curtiss Type 111872 10 lbs. (+590) c. (1) 4 Propellers - Ham. Std. hubs 43E60, blades 6903B-0 2372 lbs. (+509) (including sli ngers and shoes) Diameter: Max. 15' 1-1/16", min. allowable for repairs 14' 9-7/16". No further reduction permitted. Pitch settings at 72 in. sta.: Low fwd. 14°, low reverse -21.5°, propeller feathering pitch setting must prevent e ngine windmilling (Approximately 80.5°). Placard required in full view of flight engineer: "Airplane shall be head ed into the wind during static run-up when engine speeds exceed 2600 rpm." Max. takeoff wt. with auto -feathering inoperative - 131,500 lbs., or maximum weight with auto feathering operative whichever is less. (2) 4 Propeller spinners - Ham. Std. 83772 84 lbs. (+509) (3) 4 Propeller Feathering Pumps (a) Pesco 112577-021-01 92 lbs. (+617) (4) 4 Propeller Governors Ham. Std. Type 5AA-22-8 or 5U18 (See NOTE 20) 56 lbs. (+532) (5) 4 Synchronizing Generators Kollsman Type 1492-0120304 17 lbs. (+579) (6) 1 Synchronizing C ontrol Box Ham. Std. Dwg. 322080 40 lbs. (+193) d. (1) 4 Propellers - Curtiss electri c hubs C634S-C500, blades 2610 lbs. (+509) 830-21C4-0 (including slingers and shoes) Diameter 15'1". Pitch settings at 54 in. sta.: low fwd. 22.3° low reverse -16°, propeller feathering pitc h setting must prevent engine windmilling (approximately 90.5°). Placard required in full view of flight engineer: "Do not operate propellers in flight below 1500 engine rpm." Max. takeoff wt. autof eathering inoperative - 129,800 lbs. (2) 4 spinners - Curtiss Type 145491 84 lbs. (+509) (3) 4 Alternators - Curtiss Type 124512 16 lbs. (+545) (4) 1 Synchronizer Master Unit - Curtiss Type 119778-20 40 lbs. (+195) (5) 2 Voltage boosters - Curtiss Type 116285-231 40 lbs. (+252) (6) 1 Master Unit Filter - Cu rtiss Type 112148-9 6 lbs. (+171) (7) 4 Nacelle Filters - Curtiss Type 11872 10 lbs. (+590) 6A5 18 (e) (1) 4 Propellers - Ham. Std. hubs 43H60, blades 6959B-0 or blades 2598 lbs. (+509) 6967-0 (nickel plated) (inc luding slingers and shoes) Diameter: Max. 15' 1-5/16" , min. allowable for repairs 14' 9-3/16". No further reduction permitted. Pitch settings at 72 in. sta .: Low fwd. 14°, reverse -21.5° Propeller feathering pitch setting must prevent engine windmilling (approximately 80.5°) Max. takeoff wt. with auto feathering inoperative - 134,600 lbs. or maximum weight with auto feathering operative whichever is less. (2) 4 Propeller spinners - Ham ilton Standard 97197 70 lbs. (+509) (3) 4 Feathering pumps - Hamilton Standard 112577-041 or 112577-021 92 lbs. (+617) (4) 4 Propeller Governors - Hamilt on Standard 5AA-22-8 56 lbs. (+532) (5) 4 Synchronizing Ge nerators - Kollsman 1492-0120304 or 1492B-0120304 17 lbs. (+579) (6) 1 Synchronizing Cont rol Box - Hamilton Standard 322080 40 lbs. (+193) (f) (1) 4 Propellers - Cu rtiss electric (Dural) (a) Hubs C634D-A2, Blades 109652-12 (i ncluding blade heaters) 2988 lbs. (+509) (b) Hubs C634D-A4, Blades 109652-12 (inc luding slingers & shoes) 2934 lbs. (+509) Diameter: 15'0", min. allowable for repairs 14' 8-3/8". No further reduction permitted. Pitch settings at 54 in. st a.: low fwd. 23°, reverse -10° Propeller feathering pitch setting must prevent engine windmilling (approximately 88.6°). Placard required in full view of flight engineer: "Do not operate propellers in flight below 1400 engine rpm." Max. takeoff wt. autof eathering inoperative - 130,700 lbs. (2) 4 Propeller Spinners - Cur tiss type 152331 or 153121 158 lbs. (+509) (3) 4 Alternators - Curtiss type 124512 16 lbs. (+545) (4) 1 Synchronizer Master Unit - Curtiss type 152923 40 lbs. (+195) (5) 2 Voltage boosters - Cu rtiss type 116285 40 lbs. (+252) (6) 1 Master Unit Filter - Cu rtiss type 112148-9 6 lbs. (+171) Engines and Engine Accessories - Fuel and Oil System 100. Fuel dump valves (See NOTE 3 regarding use of dump valves) (a) Parker types 8-3046-75 (Mod. 2) and 9-946-75 (Mod. 2) (b) Parker types 8-3046-75 M3 and 9-946-75 M3 (c) Parker types 9-946-75-M3 and 1.319-54637M 101. Unusable fuel and system oil (See NOTE 1 for definition). Airplane Prop. Item Ce nter Section Center Section Model Installed Fuel Cells Aux. Oil Tank Installed Installed (a) 1049-54 1(a) No n/a 876 lbs. (+633) (b) 1(a) Yes n/a 945 lbs. (+633) (c) 1049B-55, 1(b) or (d) Yes Yes 940 lbs. (+642) (d) 1049C-55, 1(c) Yes Yes 1073 lbs. (+631) (e) 1049D-55, 1(b) or (d) No No 860 lbs. (+638) (f) 1049E-55, 1(c) No No 993 lbs. (+627) (g) or 1(b) or (d) Yes No 929 lbs. (+638) (h) 1049F-55 1(c) Yes No 1062 lbs. (+627) (i) 1049G-82, 1(e) Yes Yes 1113 lbs. (+630) (j) or 1(e) No No 1033 lbs. (+626) (k) 1049H-82 1(f) Yes Yes 975 lbs. (+641) (l) 1(f) No No 895 lbs. (+637) 102. Starters (a) Jack and Heintz Type JH6 ER - Model 1049-54 installation 105 lbs. (+585) (b) Eclipse Type 36E00-4 - Mode l 1049-54 installation 113 lbs. (+585) (c) Jack and Heintz Type JH6 ER - Models 1049B and 1049C 105 lbs. (+596) (d) Eclipse Type 36E00-4 - Models 1049-B and 1049-C 113 lbs. (+596) (e) AN 4116R6 - Model 1049B 113 lbs. (+596) (f) Jack and Heintz Type JH6CE 107 lbs. (+596) (g) Bendix Type 36E00-4B 121 lbs. (+596) 19 6A5 103. 4 Oil Coolers (a) AiResearch Type 86909- 23 - Model 1049-54 185 lbs. (+586) (b) AiResearch Type 87162-24 - M odels 1049B and 1049C 210 lbs. (+585) (c) AiResearch Type 87242-24 - M odels 1049B and 1049C 210 lbs. (+585) 104. 4 Engine-driven fuel pumps (a) Thompson Type TF-2100 - Model 1049-54 17 lbs. (+571) (b) Pesco Type 2P-771-CE-1 - Models 1049B and 1049C 17 lbs. (+583) (c) AN4102-1 - Model 1049B 17 lbs. (+583) (d) Thompson Type TF2100 17 lbs. (+583) 105. Auxiliary fuel pumps (a) 6 for tanks 1, 2, 3, 4, 2a, 3a (1) Thompson TF-52300-1 48 lbs. (+712) (b) 1 for tank No. 5 (center section) (See NOTE 7) (1) Thompson Type TF-42300-1 8 lbs. (+692) 106. 4 De-icer or vacuum pumps (a) Pesco Type 3P-485 - Mode l 1049-54 installation 40 lbs. (+586) (b) Pesco Type 3P-485 - Mode ls 1049B and 1049C 40 lbs. (+592) 107. 4 Hydraulic pumps (a) Vickers Type AA20511 - Mode l 1049-54 installation 102 lbs. (+583) (b) Vickers Type AA20510 - Mode ls 1049B and 1049C 112 lbs. (+595) (c) Vickers Type AA20513 112 lbs. (+595) 108. Auxiliary Oil pumps (See NOTE 7) (a) Pesco Type 012634-010 - hydraulic 12 lbs. (+642) (b) Pesco Type 112127-010 - electric 40 lbs. (+650) 109. Tip tank installa tion, consisting of: Two tip tank assemblies per LAC Drawing 316076 including 521 lbs. (+704) Undrainable Fuel (29 lbs .) and Unusable Fuel (34 lbs.) NOTE: When operating without tip tanks, it is necessary to correct for the addition of wing tips as follows: Two wing tips - removable (including deicer boots) 57 lbs. (+711) 110. Omitted. 111. Optional Engines (a) 4 Wright Compound 988TC18EA3 or 988TC18EA6 with 16:7 reduction gear ratio and 6.52:1 turbo drive ratio. (When these EA3: 14,580 lbs. (+554) optional engines are installed, the dash number on EA6: 14,700 lbs. (+554) the airplane model de signation becomes -03 or -06 respectively) Engine limits: (With fuel grade 115/145) (See NOTE 17 for engine limits when using low grade fuel) Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 51.0 in.Hg., 2650 rpm (2860 hp) (Straight line manifold pressure variation with altitude to 4800 ft.) 49.5 in.Hg., 2650 rpm (2920 hp) Takeoff (2 minutes at s ea level; 5 minutes at 7500 ft.; straight line variation of takeoff power time with altitude to 7500 ft.) (Sea level) 58.5 in.Hg., 2900 rpm (3400 hp) (Straight line manifold pr essure variation with altitude to 4000 ft.) 56.0 in.Hg., 2900 rpm (3400 hp) High impeller ratio 8.67:1 Maximum continuous: (10,000 ft.) 48.5 in.Hg., 2600 rpm (2410 hp) (Straight line manifold pressure variation with altitude to 16,400 ft.) 47.0 in.Hg., 2600 rpm (2450 hp) NOTE: Installation to be in accordan ce with Lockheed Service Bulletin No. 2939. When Propeller Item 1(c) is used in conjunction with the above engines, the power of ratings of the Wr ight 972TC18DA1 engine must be used. 6A5 20 (b) 4 Wright Compound 972TC18DA3 with 16:7 reduction gear ratio 14,200 lbs. (+554) and 6.52:1 turbo drive ratio Engine limits: Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 49.0 in.Hg., 2600 rpm (2700 hp) (Straight line manifold pressure variation with altitude to 5500 ft.) 53.5 in.Hg., 2900 rpm (3250 hp) High impeller ratio 8.67:1 Maximum continuous: (10,050 ft.) 48.5 in.Hg., 2600 rpm (2400 hp) (Straight line manifold pressure variation with altitude to 16,400 ft.) 47.0 in.Hg., 2600 rpm (2450 hp) NOTE: Installation to be in accordance with Lockheed Service Bulletin No. 1049/SB-2514. Landing Gear 200. 2 main gear shock struts (a) Cleveland Type 9040 - Model 1049-54 986 lbs. (+713) (b) Cleveland Type 9106 - Mode ls 1049B and 1049C 1040 lbs. (+713) (c) Cleveland Type 9106A 1048 lbs. (+713) (d) Cleveland Type 9291B 1048 lbs. (+713) 201. Nose gear shock strut (a) Cleveland Type 9054 480 lbs. (+195) 202. 4 main wheel-brake assemblies (a) 17.00-20, Type III (1) Goodyear Model LF20DHBM Wheel Assembly No. 9540552 512 lbs. (+708) * or Wheel Assembly No. 9540832 546 lbs. (+708) Brake Assembly No. 9540528 (inboard) 408 lbs. (+708) Brake Assembly No. 9540553 (outboard) 240 lbs. (+708) * or Brake Assembly No. 9540781 (outboard) 240 lbs. (+708) (2) Goodrich Model 1754M Wheel Assembly No. H-3-735M 812 lbs. (+708) Brake Assembly No. G-2-597 (2 per wheel) 240 lbs. (+708) (3) Goodyear Wheel Assembly No. 9540753 554 lbs. (+708) Brake Assembly No. 9540754 (outboard) 249 lbs. (+708) Brake Assembly No. 9540755 (inboard) 457 lbs. (+708) (4) Goodrich Wheel Assembly No. H-3-772 884 lbs. (+708) Brake Assembly No. G-2-639 (2 per wheel) 264 lbs. (+708) 203. 4 main wheel tires and tubes Type III (a) 17.00-20, 20-ply rating nylon (Use actual weight) Maxi mum, incl. air 884 lbs. (+708) (b) 17.00-20, 22-ply rating nylon (Use actual weight) Maxi mum, incl. air 884 lbs. (+708) 204. 2 Nose wheel assemblies (a) 4x9.9, Type VII (1) Goodrich Assembly No. H-3-592M-1 (no fairing) 68 lbs. (+184) (2) Goodrich Assembly No. H-3-592M (with fairing) 74 lbs. (+184) (3) Goodrich Assembly No. H-3-753 (no fairing) 73 lbs. (+184) (b) 33", S.C., Type I (1) Bendix Assembly No. 57608M 62 lbs. (+184) 205. 2 Nose wheel 10- ply rating nylon tires (a) 34x9.9, Type VII B (with regul ar tubes) Use actual weight) (+184) (b) 33", S.C., Type I (with regul ar tubes) Use actual weight (+184) 206. 2 Main gear drag strut dampers (a) L.A.C. Dwg. No. 307503 176 lbs. (+701) (b) L.A.C. Dwg. No. 310618 180 lbs. (+701) (c) L.A.C. Dwg. No. 469080 185 lbs. (+701) 21 6A5 Electrical Equipment 300. Generators (a) 4 D.C. Eclipse Type 30E02 - Model 1049-54 installation 254 lbs. (+584) (b) 4 D.C. Eclipse Type 30E02 - Model 1049B and 1049C 254 lbs. (+597) (c) 6 D.C. Eclipse Type 30E02-(9) 381 lbs. (+594) 301. Batteries (a) 2 24 Volt, 36 A.H. 152 lbs. (+283) 303. Alternators (a) 2 Pioneer Type 1631-7 19 lbs. (+588) (b) 2 Pioneer Type 1632-1 12 lbs. (+588) (c) 2 Eclipse Type 28E04 21 lbs. (+601) (d) 2 Eclipse Type 28E04 21 lbs. (+582) (e) Inverter (Bendix Model K-2496) 13 lbs. (+130) Interior Equipment 400. FAA Approved Airplane Fli ght Manual. (A manual containing information required for the Airplane Flight Manual may be carried in lieu thereof in aircraft operated under the provisions of Parts 40, 41 and 42 of the Civil Air Regulations.) The following table identif ies the airplane flight manuals and revisions thereto currently approved for each airplane: Lockheed Date of Serial Report Latest For Aircraft Model Number Number Revision with Item: 1049-54 4001 thru 4024 7787 4-14-58 1049B-55 4101 thru 4111 (All of these se rial numbered aircraft delivered 4122 thru 4130 as Model R7V-1 or C121C. Approved Manuals must 4133 thru 4150 be provided at tim e of conversion to Model 1049B-55 4152 thru 4160 or 1049F-55 per NOTE 5(d).) 4167 thru 4169 1049F-55 4170 thru 4202 1049C-55 4503, 4504, 4506 9153 6-27-58 1(b) or 1(d) 1049E-55 4507, 4509 thru 9154 5-29-58 1(c) 1049E/01-55 4552, 4554 thru 1049E/02-55 4557, 4561 thru 4565, 4573, 4574 4578 thru 4581, 4606, 4607, 4613 thru 4615 . 1049G-82 4572, 4575 thru 10051 (with 10-1-58 1(f) 4577 Log of Pages i) 4553, 4558, 4559, 4560, 10051 (with 4629, 4630, 4631, 4635 Log of Pages Ai) 4641, 4643 10051 (with Log of Pages Bi) 4682, 4683 10051 (with Log of Pages Ci) 4679, 4680 10051 (with Log of Pages Di) 1049C-55 4501, 4502, 4505, 10051 (with Modified to 4508 Log of Pages Ei) 1049G/02-82 1049G-82 4582 thru 4601, 10052 (with 10-1-58 1(e) 4648 thru 4652, Log of Pages i) 4654, 4656, 4658 4602 thru 4605, 10052 (with 4637, 4640, 4642, Log of Pages Ai) 4647 4610 thru 4612 10052 (with Log of Pages Bi) 4620 thru 4627, 10052 (with 4668 thru 4671, Log of Pages Ci) 4634, 4639 6A5 22 Lockheed Date of Serial Report Latest For Aircraft Model Number Number Revision with Item: 4616 thru 4618 10052 (with Log of Page Di) 4628, 4646, 4666, 10052 (with 4667, 4686, 4687 Log of Pages Ei) 4619 10052 (with Log of Pages Fi) 4636, 4674 10052 (with Log of Pages Gi) 4644, 4645 10052 (with Log of Pages Hi) 4653, 4655, 4657, 10052 (with 4659 thru 4665 Log of Pages Ji) 4673, 4676 10052 (with Log of Pages Ki) 4672, 4677, 4678 10052 (with Log of Pages Li) 4681, 4684, 4685 10052 (with Log of Pages Mi) 4632, 4633, 4675 10052 (with Log of Pages Ni) 1049D/01-82 4165, 4166 11020 (with 1-12-59 1(b) Log of Page i) 1049H 4801, 4803 11020 (with 10-1-58 1(f) Log of Pages Ai) 4802, 4805 thru 11020 (with 1-12-59 1(b) 4808 Log of Pages Bi) 4828, 4829, 4831, 11020 (with 10-1-58 1(c) or 1(e) 4832 Log of Pages Fi) 1049H/01-03 4839, 4842, 4844, 11020 (with 10-23-58 or 4845 Log of Pages Ci) 1049H/01-03 4804, 4809 thru 4812, 11020 (with Modified to 4814, 4815, 4816, Log of Pages Di) 1049H/02-03 4819, 4822, 4827, 1049H/05-03 4852, 4853 1049H/06-03 4813, 4817, 4818, 4820, 11020 (with 4821, 4823 thru 4826 Log of Pages Ei) 4830 11020 (with Log of Pages Gi) 4833, 4834, 4837, 11020 (with 4838 Log of Pages Hi) 4835, 4836 11020 (with 1(f) Log of Pages Ji) 4840, 4841, 4843 11020 (with 1(c) or 1(e) Log of Pages Li) 4846, 4847 11020 (with Log of Pages Mi) 1049D/01-82 4163, 4164 11020 (with 1-12-59 1(b) Modified to Log of Pages Ki) 1049H/03-82 1049H/02-03 4850, 4851 11020 (with 1-12-59 Modified to Log of Pages Ni) 1049H/07-03 23 6A5 401. Surface Control Equipment (a) Automatic pilot (1) Pioneer PB-10 (3 servos 15601-1A, 1 servo 15620-2A) 141 lbs. (+700) NOTE: The following informati on may be used with Model 1049 only. When using automatic pilo t in cruise configurations, minimum terrain clearance is 500 ft. When using automatic pilot during approach, mini mum altitude is 200 ft., pilot's seat belt fastened and ha nd on control wheel. (Minimum altitude for each case does not overrule any higher minimum operational altitude.) (Maximum speed for autopilot is 338 MPH) Servo stall forces measur ed at the pilot's controls: Elevator 30 lbs. +0 lbs. -10 lbs. Aileron 30 lbs. +0 lbs. -10 lbs. Rudder 95 lbs. +0 lbs. -30 lbs. (These forces have not been de monstrated for Flight Path Control) (2) Pioneer PB-10 (3 servos 15601-1A or 15613-1, 1 servo 15620-2A.) 141 lbs. (+700) Maximum speed for operati on with autopilot is 338 MPH (294 knots.) (See FAA Approved Airplane Flight Manual for altitude loss during autopilot malfunction.) Torques Measured at Component Servo Stall Forces Measured Servos with Control at Pilot's Controls Cable Disconnected Elevator 40 lbs. +0 lbs., -14 lbs. 310 in. lbs. + 10% Aileron 19 lbs. +0 lbs., - 6 lbs. 225 in. lbs. + 10% Rudder 80 lbs. +0 lbs., -30 lbs. 400 in. lbs. + 10% (These forces are satisfactory for Flight Path Control) *(3) Lear L-5 in accord ance with Lear Dwg. 700062 (3 main servos 183 lbs. (+687) 118AP, elevator a nd rudder trim service 2216A). Maximum speed for operati on with autopilot is 325 mph. (See FAA approved Lear Airpla ne Flight Manual Supplement for altitude loss during autopilot malfunction). Servo torques measured in in. lbs. at the servos: Rudder 280 max. 225 min. Aileron 175 max. 140 min. Elevator 182 max. 154 min. (These torques are satisfactory for automatic approach) (b) Elevator boost unit - P/N 308575 or 322645 108 lbs. (+1420) (c) Rudder boost unit - P/N 308576 or 322646 105 lbs. (+1417) (d) 2 Aileron boost units P/N 289283-602 71 lbs. (+734) 420. 2 cabin superchargers (a) AiResearch Type 56930 (with snood) 187 lbs. (+634) (b) Airesearch Type 57910 193 lbs. (+634) (c) AiResearch Type 57910B 202 lbs. (+642) (d) Airesearch Type 57970 421. 2 Supercharger drive sh aft and disconnect assemblies (a) LAC 31145 shaft assembly a nd guard installation per LAC Dwg. No. 308479 109 lbs. (+613) (b) LAC 311442 shaft assembly and guard installation per LAC Dwg. No. 311441 100 lbs. (+617) (c) LAC 315908 shaft assembly a nd guard installation per LAC Dwg. No. 315904 82 lbs. (+620) (d) LAC 329552 shaft assembly and guard installation per LAC Dwg. No. 315904 82 lbs. (+620) (e) L.A.C. 469864 shaft assembly and guard installation per LAC Dwg. No. 470286. 82 lbs. (+620) (f) L.A.C. 470093 shaft assembly and guard installation per LAC Dwg. No. 470286. 82 lbs. (+620) 6A5 24 (g) AiResearch 205400 shaft and guard insta llation per LAC Dwg. No. RR1393 80 lbs. (+620) 422. 2 Cabin heaters (a) Surface combustion Type A77A63 42 lbs. (+800) 423. 2 Recirculating fans (a) Dynamic Air Type 8862B-8B 74 lbs. (+800) (b) Joy Type X702-164 70 lbs. (+800) 424. Cabin refriger ation installation (a) 2 Cooling units, AiResearch Type 56910-1 and 2 47 lbs. (+744) (b) 2 Heat exchange cooling blower s, AiResearch Type 30980 45 lbs. (+759) (c) 2 Primary heat exchangers, AiResearch Type 19658 70 lbs. (+740) (d) 2 Secondary heat exchangers, AiResearch Type 81118 82 lbs. (+747) (e) 2 Water separators, AiResearch Type 81148-3 and -4 39 lbs. (+730) 440. Emergency ladder or emergency chute See Approved Master Equipmen t List for approved locations, types, weights and arms for various configurations. 441. Fixed Oxygen system (a) Model 1049-54 installed in accordan ce with LAC Dwg. No. 309287, including: (1) One Kidde Type 870324 cylinder 27 lbs. (+26) (2) 3 Masks (full face or ova l-nasal with goggles) Negligible (b) Model 1049-54 installe d in accordance with LAC Dwg. No. 311142, including: (1) 3 Kidde Type 870326 cylinders LAC Dwg. No. 654112 177 lbs. (+254) (2) 3 Masks, TWA 1-45981-1 Negligible (c) Model 1049C-55-81 installed in accordance with LAC Dwg. No. 313262, including: (1) 2 Kidde Type 870275 cylinders LAC Dwg. No. 654092 68 lbs. (+218) (d) Model 1049C-55-81 installe d in accordance with LAC Dwg. No. 318611, including: (1) One Kidde Type 870326 cylinder LAC Dwg. No. 654112 63 lbs. (+218) (e) Model 1049B-55-75 installe d in accordance with LAC Dwg. No. 311168, including: (1) 3 Kidde Type 870557 cylinders LAC Dwg. No. 654114 69 lbs. (+224) (f) Model 1049C-55-94 installed in accordance with LAC Dwg. No. 321501, including: (1) One Kidde Type 870 cylinder (LAC Dwg. NO. 654092) 34 lbs. (+231) (g) Model 1049D-55-85 installed in accordance with LAC Dwg. No. 322662, including: (1) 1 Kidde Type 870275 (h) Model 1049G-82-101 installed in accordance with LAC Dwg. No. 465081 including: (1) 2 Kidde Type 870326 cylinders LAC Dwg. No. 654112 125 lbs. (+215) (i) Model 1049G-82-102 installe d in accordance with LAC Dwg. No. 328201 including: (1) 2 Kidde Type 870275 cylinders LAC Dwg. No. 654092 68 lbs. (+218) (j) Model 1049F-55-96 installed in accordance with LAC Dwg. No. 315939, including: (1) Three Kidde Type 870275 cylinders (LAC Dwg. No. 654114) 69 lbs. (+224) (k) Model 1049H-82-133 installe d in accordance with LAC Dwg. No. 496938, including: (1) Two Kidde Type 870275 cylinders LAC Dwg. No. 654092 64 lbs. (+219) De-icing Equipment 500. Wing de-icer boots (a) Goodrich Type 21 Pneumatic 150 lbs. (+642) (b) Goodrich Type 22 Pneumatic 165 lbs. (+640) 501. Stabilizer de-icer boots (a) Goodrich Type 21 Pneumatic 68 lbs. (+1345) (b) Goodrich Type 22 Pneumatic 76 lbs. (+1345) 502. Fin de-icer boots (a) Goodrich Type 21 Pneumatic 39 lbs. (+1365) 25 6A5 508. Windshield wipers (a) 1 Dual Marquette (electric) in stalled in accordance with 17 lbs. (+189) LAC Dwg. No. 309368 (b) 1 Dual Marquette installed in accord ance with LAC Drawing No. 325296 18 lbs. (+189) (c) 1 Dual Alco installed in accordan ce with LAC Dwg. No. 326072 13 lbs. (+183) (d) 2 wipers Alco installed in accord ance with LAC Dwg. No. 327329 11 lbs. (+163) NOTE 1. (a) Current weight and balance re port including list of equipment included in certificated weight empty, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). See approved Master Equipment List (LAC Report 8097) for list of approved items of equipment in addition to those items listed in this specification. (b) The airplane must be load ed so that the C.G. is within the specified limits at all times, with the effects of fuel use, gear retraction, and moveme nt of crew and passengers from their assigned positions being considered (retraction of the main and nose gears causes the C.G. to move forward, a value of 186,000 in. lbs. is a satisfactory approximation of the cha nge in moment for all approved wheel items). At takeoff, the airplane shall be loaded so that, due to fuel use, the C.G. cannot move forward of 18% MAC. A 34% aft C.G. limit (gear retracted) for cruising flight may be used when the effect of passenger and crew movements from their assigned positions has been taken into account. (c) "Unusable Fuel and System Oil" and all hydraulic fluid must be included in the certificated weight empty. (See Item 101) Unusable fuel is that quantity of fuel in the system and in the tanks which is unavailable to the engines under critical flight conditions as de fined in CAR 4b.494. Thus unusable fuel, includes "system fuel" which is defined as the quantity required to fill the system and tanks to the tank outlet level when the airplane is in the ground level attitude. The fuel gages are calibrated with the unus able fuel level as the zero datum. The total amount of fuel (Unusable included in Item 101) is as follows: Model Center Section Fuel Cells Installed Usable Fuel (lbs.) Unusable Fuel (lbs.) 1049-54 Yes 39,300 491 No 34,920 422 1049B-55** or 1049C-55** Yes 39,300* 457 or 1049D-55** No 34,920* 388 or 1049E-55** or 1049F-55** or 1049G-82** or 1049H-82** 1049G-82, 10498-82 with tip tanks Yes 46,608 520 *The total usable fuel must be limited to 28,800 lbs. when the oil transfer system is not installed (See NOTE 7). ** No tip tanks (See ITEM 109). System oil is that amount of oil required to fill the oil systems and tanks to the tank outlets to the engines. The propeller feathering oil is not cons idered usable oil, and, when applicable, is included in "System oil." The oil tank capacities shown in this specification include only the usable oil for which the tanks are placarded. Dipstick readings indicate the amount of usable oil. Model With Aux. Oil Tanks With Oil Transfer System Prop. Item Installed Usable Oil (lbs.) System Oil (lbs.) or 1049-54 Yes --- 1(a) 1740 454 No --- 1(a) 1650 454 1049B-55 --- Yes 1(b) or (d) 1702 483 or 1049C-55 --- Yes 1(c) 1702 616 or 1049D-55 --- No 1(b) or (d) 1200 472 or 1049E-55 --- No 1(c) 1200 605 or 1049F-55 --- 1049G-82 --- Yes 1(e) 1702 656 or 1049H-82 --- Yes 1(f) 1702 518 No 1(e) 1200 645 No 1(f) 1200 507 6A5 26 (d) Fuel dumping. When fuel dump valves (Item 100) are installed per NOTE 3, the amount of usable fuel, over and above the unusable fuel listed in Item 101, remaining after dumping is as follows: Gallons Remaining in Tanks (A) Model Tank 5 Tanks 2 & 3 Tanks 1 & 4 Tanks 2a & 3a Tanks 1a & 4a Remarks 1049-54 - 45 ea. 139 ea. 152 ea. - 1049B-55 See 45 ea. 145 ea. 149 ea. - No standpipes in Tanks 2 & 3 - 4" connector 1049C-55 Foot- 145 ea. 145 ea. 149 ea. - (D) Standpipes installed in Tanks 2 & 3 - 4" connector 1049D-55 note 174 ea. 145 ea. 149 ea. - (D) Standpipes installed in Tanks 2 & 3 - 2-1/2" connector 1049E-55 or 1049F-55 Below 71 ea. 145 ea. 149 ea. - No standpipes in Tanks 2 & 3 - 2-1/2" connector 1049G-82 45 ea. (C) 175 ea. (C) 175 ea. - No Standpipes in Tanks 2 & 3 - 4" connector 1049H-82 145 ea. (C) 175 ea. (C) 175 ea. - (D) Standpipes installed in Tanks 2 & 3 - 4" connector 1049G-03 or 1049H-03 1049G-82 45 ea. (C) 175 ea. (C) 175 ea. 15 ea. No Standpipes in Tanks 2 & 3 - 4" connector 1049H-82 145 ea. (C) 175 ea. (C) 175 ea. 15 ea. (D) Standpipes installed in Tanks 2 & 3 - 4" connector 1049G-03 or 1049H-03 The indicated combinations of undumpable fuel and the corresponding st andpipe arrangement apply to any model within a given block. (Same as amount prior to dumping (no dump valves in this tank). Standpipe height increased to accommodate EA-3 engines. Operational zero fuel weight must not exceed the design landing weight minus the total undumpable fuel weight (including fuel in tank No. 5 at take-off), but in any case must not exceed design zero fuel weight. (The above undumpable fuel quantities at 6 lbs. per gallon should be used in this determination). (e) Fuel loading and usage. (1) Fuel must be distributed a nd used in a manner that will permit compliance with the lateral balance limitations in the FAA Appr oved Airplane Flight Manual. (2) For minimum fuel at any takeo ff weight, refer to fuel loading and usage chart in the pertinent Approved Operating Manual. (3) Fuel loaded in Tank No. 5 will affect the maximum zero fuel gross weight as follows: Model Maximum Zero Fuel Weight 1049-54 93,500 lbs. less weight of fuel in Tank 5 or 95,500 lbs. less weight of fuel in Tank 5 (see Note 6) 1049B-55 105,000 lbs. less weight of fuel in Tank 5 or 1049F-55 1049C-55 103,500 lbs. less weight of fuel in Tank 5 in excess of 1500 lbs. or 1049E-55 or 1049G-82 1049D-55 105,000 lbs. less weight of fuel in Tank 5 or 1049D/01-55 108,000 lbs. less weight of fuel in Tank 5 or 1049H-82 (See Note 11) 1049G-82 with tip tanks 104,200 lbs. less weight of fuel in Tank 5 27 6A5 (4) By reason of structural limitations, the followi ng fuel quantities shall not be exceeded during landing operations: Model Tank 5 Tanks 2 & 3 Tanks 1 & 4 Tanks 2a & 3a Tanks 1a & 4a 1049-54 730 gal. 790 gal. ea. 1200 gal. ea. 515 gal. ea ---- 1049-55 or 1049C-55 No limitations. ----- or 1049D-55 (Tanks 2a and 4a not installed) ----- or 1049E-55 ----- or 1049F-55 or 1049G-82 or 1049H-82 ----- 1049G-82 730 gal. 790 gal. ea. 1555 gal. ea 565 gal. ea. 200 gal. ea. NOTE 2. The following placards must be installed: (a) In full view of the pilots and flight engineer: (1) "This airplane must be fueled and the fuel used in accordance with instructions contained in the FAA approved Airpla ne Flight Manual." (2) "This airplane shall be opera ted in accordance with the Operating Limitations specified in the FAA Approved Airpla ne Flight Manual." (b) On the forward side of door at Station 303.5 for th e -67 interior, or door at Station 339 for -81 interior: "This door must be locked open during all take-offs and landings." NOTE 3. Fuel dump valves (Item 100) must be installed for operation of the airplane at weights in excess of maximum landing weight. Refer to CAA Approved Airpla ne Flight Manual for limitations and cautionary procedures to be observed during the dumping of fuel. NOTE 4. The electric drive on the elevator trim tab mechanism on the control pedestal, formerly considered as an integral part of the airplane, may be retained or removed at the option of the operator. NOTE 5. Prior to civil certification of each military R7V-1 or C121-C aircraft of the Model 1049B-55 or 1049F-55 series, the following modifications will be required: (a) The position and fuselage light s installation must be modified to conform to FAA requirements. (b) On R7V-1 aircraft, fire detec ting and extinguishing equipment must be installed in the lower baggage compartments in accord ance with CAR 4b.383(c). (c) All military special equipment must be removed. (d) FAA approved operating manua l (Airplane Flight Manual) (Item 400) must be provided. (e) Airplanes bearing manufacturer's numbers 4102, 4103, 4104 and 4106 must be inspected for corrosion of the integrally stiffened machined plates of the inner wing lower surface. In order to accomplish this, the sealing of integral fuel tanks in this area must be removed. If detrimental corrosion is found, contact Lockheed Aircraft Corporation for corrective measures. (f) Parachute flares must be installed. (g) Airspeed placards limiting Vno and Vn e in accordance with airspeed limits of Part III of this specification must be installed in fu ll view of the pilots. (h) Placards must be installed in th e cabin which will insure that an aisle way will be maintained throughout the entire length of the cabin to: (1) Provide access to an emergency ex it over the wing for smoke evacuation purposes. (2) Provide access to all cargo in the cabin area to facilitate fire fighting with a hand extinguisher. (i) Placards must be installed to wa rn ground and flight personnel that the ai rplane must not be flown with the cargo doors removed or unlatched. (j) Revise the engine nameplate to include the corresponding civil model designation (972TC18DA1) and Type Certificate No. (272). (k) Compliance with Airwor thiness Directive Note No. 55-23-2 or Lockheed Service Bulletin No. 1049/SB-2753 must be accomplished for Serial Nos. 4144 and up. NOTE 6. Lockheed Serial Nos. 4101 through 4139 of Model 1049B (Navy R7V-1) are eligible for certification at 130,000 pounds takeoff weight only. To be eligible for certification at 133,000 pounds takeoff weight, the following items must be accomplished: (1) Fuel loading and usage procedure must be in acco rdance with that described in Lockheed Report No. 9154. 6A5 28 (2) Reinforce fuselage main frame and fuselage skin in accordance with Lockheed Rapid Revision Dwg. No. 173. NOTE 7. When auxiliary oil tank and oil transfer systems are not used on Model 1049B-55 and 1049C-55, total usable fuel must be limited to 4800 gallons (28,800 lbs.). NOTE 8. Model 1049-54 aircraft are eligible for certification at a landing weight of 101,500 lbs. and a maximum zero fuel weight of 95,500 lbs. when modified in accordan ce with Lockheed Service Bulletins No. 1049/SB2202, 1049/SB2223 and 1049/SB2224. These modifica tions include reinforcements of the fuselage and wings, revised orifice plates in the main landing gear oleos, and revised piston assemblies in the main landing gear drag link shock struts. NOTE 9. If cargo aircraft (Model 1049B-55 or 1049F-55) are converted for passenger operation or combination passenger- cargo operation, approved modi fications must be incorporated to show compliance with CAR 4b.433, 4b.434 and SR389 effective October 27, 1952, or Ame ndment 4b-4, effective December 20, 1951. NOTE 10. In accordance with the agreement between the Department of Defense and the Civil Aeronautics Board, all air carrier operators utilizing aircraft wh ich have been modified under the Civil Reserve Air Fleet Program, Part I, Phase II, may deduct the added weight of the military m odification up to a maximum of 50 pounds for each aircraft so modified. NOTE 11. Model 1049D-55 is eligible for landing weight of 113,000 lbs., takeoff weight of 135,400 lbs., and maximum zero fuel weight of 108,000 lbs., when larger brakes are installed, stronger main landing gear side struts and drag strut dampers are installed and other minor modifications accomplished. These changes are described in Lockheed Service Bulletin 2373, 2504, 2508, 2509, 2529 and 2599. Upon comp letion of all of these items, the airplane is re- designated as Model 1049D/01-55. NOTE 12. Models 1049C-55 and 1049E-55 are eligible for a takeoff weight of 135,400 lbs. when stronger main landing gear side struts and drag strut dampers, speed recovery modifications, propeller spinner afterbodies, fuselage and wing reinforcements and propeller blade tr ailing edge fairings (on those airplanes having Curtiss 858 propellers) are installed. Lockheed Servi ce Bulletin 2300, 2301, 2302, 2303, 2329, 2330, 2500, 2508, 2509 and 2599 describe those modifications required fo r Model 1049C. Service Bulletins 2500, 2508, 2509 and 2599 describe those required for Model 1049E. Upon completion of all of thes e items, the airplane is re-designated as Model 1049E/01-55. NOTE 13. Model 1049E/01-55 (See NOTE 12) is eligible for a landing weight of 113,000 lbs. when the landing gear incorporates wheel and brake assemblie s as described under equipment items 202(a)(3), or (a)(4). The airplane is then designated as Model 1049E/02-055. NOTE 14. Model 1049H-82 is eligible for increased takeoff, landing and zero fuel weights when certain specific modifications are incorporated. Upon completion of the required items the aircraft model is redesignated. The redesignated aircraft with the required modifications and weight limitations are listed below. A. Model 1049H/01-03 or 1049H/01-06 This model is basically a 1049H with the wing st ructure reinforced according to Lockheed Drawing No. 329998-505 "Wing Group Inst allation" and Item 111 (a) optional engines and propeller Item 1(e) are installed. Tip Tanks Off Tip Tanks On Gross Weight 140,000 140,000 Landing Weight 113,000 113,000 Zero Fuel Weight 109,500 106,700 B. Model 1049H/02-03 or 1049H/02-06 This model is a 1049H/01 modified in accordance with Lockheed Service Bulletin No. 3041. This results in a change in landing weight to 114,500 lbs. for both tip tanks on or off configurations. C. Model 1049H/03. See NOTE 18. D. Model 1049H/04-82 This model is basically a 1049H m odified in accordance with Lockheed Service Bulletin No. 3041 making this model eligible for the followi ng landing and zero fuel weights: Tip Tanks Off Tip Tanks On Landing Weight 114,500 114,500 29 6A5 Zero Fuel Weight 109,500 104,200 E. Model 1049H/05-03 or 1049H/05-06 This model is basically a 1049H/01 modified in accordance with Lockheed Service Bulletin No. 3060 rendering this model eligib le for the following weights: Tip Tanks Off Tip Tanks On Takeoff Weight 142,100 142,100 Landing Weight 113,000 113,000 Zero Fuel Weight 108,000 108,000 F. Model 1049H/06-03 or 1049H/06-06 This model is basically a 1049H/06 modified in accordance with Lockheed Service Bulletin No. 3060 rendering this model eligib le for the following weights: Tip Tanks Off Tip Tanks On Takeoff Weight 142,100 142,100 Landing Weight 114,500 114,500 Zero Fuel Weight 109,500 109,500 G. Model 1049H/07-03 or 1049H/07-06 This model is basically a 1049H/06 with the takeoff weight limited because of the substitution of propeller Item 1(b) for Item 1(e). Th e operational weights are as follows: Tip Tanks Off Tip Tanks On Takeoff Weight 141,700 141,700 Landing Weight 114,500 114,500 Zero Fuel Weight 109,500 109,500 NOTE 15. The 975C18CB1 engine is eligible for use with grade 100/130 or 108/135 fuel at the following ratings: Lower impeller ratio 6.46:1 Maximum continuous: (Sea level) 43.5 in.Hg., 2600 rpm (2150 hp) (Straight line manifold pressu re variation with altitude to 8700 ft.) 40.5 in.Hg., 2600 rpm (2150 hp) Takeoff (2 minutes): (Sea level) 47.0 in.Hg., 2600 rpm (2350 hp) (Straight line manifold pressu re variation with altitude to 5900 ft.) 45.0 in.Hg., 2600 rpm (2350 hp) High impeller ratio 8.67:1 Maximum continuous: (14,000 ft.) 42.0 in.Hg., 2600 rpm (1800 hp) (Straight line manifold pressure variation with altitude to 18,800 ft.) 41.0 in.Hg., 2600 rpm (1800 hp) When using the above grade fuel and power rati ngs, the airplane weight limitations are as follows: Landing: 91,000 lbs. Takeoff 100,000 lbs. (Dump valves are required) Maximum zero fuel weight: 87,332 lbs. NOTE 16. The 972TC18CDA1 engine is eligible for use with grade 100/130 or 108/135 fuel at the following ratings with automatic rich mixture settings onl y for all operations including cruise:: Lower impeller ratio 6.46:1 Maximum continuous: (Sea level) 43.5 in.Hg., 2600 rpm (2380 hp) (Straight line manifold pressu re variation with altitude to 9100 ft.) 41.0 in.Hg., 2600 rpm (2450 hp) Takeoff (2 minutes at s ea level; 5 minutes at 7500 ft. (Straight line variation of take off power time with altitude to 7500 ft.) (Sea level) 51.0 in.Hg., 2900 rpm (2880 hp) (Straight line manifold pressu re variation with altitude to 8100 ft.) 47.5 in.Hg., 2900 rpm (2950 hp) 6A5 30 High impeller ratio 8.67:1 Operation with grade 100/130 fuel not permitted. When using the above grade fuel and power rati ngs, the airplane weight limitations are as follows: Landing: 101,500 lbs. Takeoff 120,000 lbs. (Dump valves are required) Maximum zero fuel weight: 95,884 lb s. (with 2-1/2 inch connector tubes) 95,560 lbs. (with 4 inch connector tubes) NOTE 17. The 972TC18DA3, 988TC18EA3 a nd 988TC18EA6 engines are eligible for use with grade 100/130 or 108/135 fuel at the following ratings with au tomatic rich mixture settings only for all operations including cruise:: Lower impeller ratio 6.46:1 Maximum continuous: (Sea level) 44.0 in.Hg., 2600 rpm (2380 hp) (Straight line manifold pressu re variation with altitude to 9400 ft.) 41.5 in.Hg., 2600 rpm (2450 hp) Takeoff (2 minutes at s ea level; 5 minutes at 7500 ft.; straight line variation of take off power time with altitude to 7500 ft.): (Sea level) 51.0 in.Hg., 2900 rpm (2880 hp) (Straight line manifold pressu re variation with altitude to 8500 ft.) 48.0 in.Hg., 2900 rpm (2950 hp) High impeller ratio 8.67:1 Operation with grade 100/130 fuel not permitted. When using the above grade fuel and power ratings, the airplane weight limitations are as follows: Landing: 101,500 lbs. Takeoff 120,000 lbs. (Dump valves are required) Maximum zero fuel weight: 96,750 lbs. (Tip tanks off) Standard configuration) 96,580 lbs. (Tip tanks on) 95,560 lbs. (Tip tanks o ff and stand pipe in tanks 2 and 3) 95,380 lbs. (Tip tanks on and stand pipe in tanks 2 and 3) NOTE 18. Model 1049D/01 may be modified to Model 1049H when modified in accordance with Lockheed Service Bulletin No. 2505. Upon completion of this item, th e airplane is redesignated as 1049H/03-82. NOTE 19. In accordance with Civil Aeronautics Board Special Regulation 411A, aircraft operated by "Air Carriers" for cargo operation only, are permitted to increase the zero fuel we ight and landing weight by 5 per cent of the zero fuel weight. For aircraft covered by this specification, the landing and maximum zero fuel weights may be increased as follows for airplanes equipped with Hamilton Standard and Dural propellers and with 858 trailing edge propellers, respectively: Tip Tanks Landing Weight Zero Fuel Weight ON OFF ON OFF Hamilton Standard Propellers (Equipment Items 1(c) and 1(e)) Model 1049C & ) (1) 115,210 115,175 109,410 108,675 1049E & 1049E/01) (2) 115,210 115,175 109,090 108,675 1049E/02 (1) 117,200 117,200 109,410 108,675 (2) 117,200 117,200 109,410 108,675 1049G (equip. item 1(e) only) 118,210 118,175 109,410 108,675 1049H 118,210 118,400 109,410 113,400 1049H/01 118,335 118,400 112,035 113,400 1049H/02 119,835 119,975 112,035 114,975 1049H/05 118,400 118,400 113,400 113,400 1049H/06 119,975 119,975 114,975 114,975 31 6A5 Tip Tanks (cont'd) Landing Weight Zero Fuel Weight ON OFF ON OFF Dural Propellers (Equipment Item 1(f)) Model 1049C & ) (1) 115,210 115,175 109,410 108,675 1049E & 1049E/01) (2) 115,210 115,175 109,090 108,675 1049E/02 (1) 116,600 116,600 109,410 108,675 (2) 116,600 116,600 109,410 108,675 1049G 117,600 117,600 109,410 108,675 1049H 117,600 117,600 109,410 112,860 1049H/01 118,335 118,400 112,035 113,400 1049H/02 119,835 119,975 112,035 114,975 1049H/05 118,400 118,400 113,400 113,400 1049H/06 119,975 114,975 114,975 114,975 858 T.E. Propellers (Equipment Item 1(b)) Model 1049C & (1) 115,210 115,175 109,410 108,675 1049E & 1049E/01 (2) 115,210 115,175 109,090 108,675 1049E/02 (1) 115,600 115,600 109,410 108,675 (2) 115,600 115,600 109,410 108,675 1049D/01 115,600 115,600 109,410 111,220 1049H 116,850 116,850 109,410 112,110 1049H/03 116,850 116,850 109,410 112,110 1049H/07 118,800 118,800 113,880 114,060 (1) Standpipes in tanks 2 and 3 with 2-1/2" connecting tube. (2) Standpipes in tanks 2 a nd 3 with 4" connecting tube. In addition to the operator's normal inspection program, aircraft operated in accordance with SR-411A must be inspected with the "Ins pection Procedures for Cargo Aircraft Operated at Gross Weights Above Certificated Gross Weights" (Lockheed Report No. 11414, Pages 27 and 28) as revised and approved by the FAA. Requests for changes in the inspection procedure must be forwarded to the manufacturer for his recommendations and submittal to the FAA for approval. The increased weights authorized in acco rdance with SR-411A do not apply to foreign operators when the aircraft is operated in the United States. FAA Approved Airplane Fli ght Manual revision, including performance information for operation at the increased weights, should be obt ained from the manufacturer or from the organization performing the modifications for cargo operation and submitting the corresponding Manual Supplement for FAA approval. NOTE 20. Propeller governor Type 5U18 is eligible for use only on aircraft equipped with Wright 975C18CB-1 engines. -END- ``` ## ADs (41, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993 - [AD 71-07-02](https://openairdocs.org/ad/71-07-02): Obstacle Clearance Profile · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 12 more. Effective Apr 3, 1971 - [AD 67-03-05](https://openairdocs.org/ad/67-03-05): Propeller Vibratory Stresses · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 9 more. Effective Jan 23, 1967 - [AD 65-13-06](https://openairdocs.org/ad/65-13-06): Wing Rear Beam Cap Tie-In Fittings · Lockheed 1049C-55, 1049D-55, 1049E-55 and 2 more. Effective Jul 23, 1965 - [AD 65-11-03](https://openairdocs.org/ad/65-11-03): Radio Transfer Switch Aassembly · Lockheed 1049C-55, 1049E-55, 1049G-82 and 1 more. Effective May 20, 1965 - [AD 64-13-03](https://openairdocs.org/ad/64-13-03): Nose Landing Gear Rod Ends · Lockheed 1049-54, 1049C-55, 1049D-55 and 9 more. Effective Jun 12, 1964 - [AD 64-07-04](https://openairdocs.org/ad/64-07-04): Flight Control Boost Systems · Lockheed 1049-54, 1049C-55, 1049D-55 and 9 more. Effective Apr 14, 1964 - [AD 64-02-05](https://openairdocs.org/ad/64-02-05): Openable Window in the Crew Exit · Overhead emergency exit hatch between fuselage station 278.4… (Flying Tiger Line STC SA4-948). Effective Jan 10, 1964 - [AD 63-25-02](https://openairdocs.org/ad/63-25-02): Nose Landing Gear · Lockheed 1049-54, 1049C-55, 1049D-55 and 9 more. Effective Dec 30, 1963 - [AD 62-27-07](https://openairdocs.org/ad/62-27-07): Wing Front Spar Lower Cap and Web · Lockheed 1049C-55, 1049D-55, 1049E-55 and 2 more. Effective Jan 28, 1963 - [AD 62-26-03](https://openairdocs.org/ad/62-26-03): Main Landing Gear Crossheads · Lockheed 1049-54, 149-46, 49-46 and 4 more. Effective Jan 7, 1963 - [AD 62-16-03](https://openairdocs.org/ad/62-16-03): Wing Rear Spar Upper Cap · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 5 more. Effective Aug 13, 1962 - [AD 62-01-02](https://openairdocs.org/ad/62-01-02): Main Landing Gear Cylinders · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more. Effective Jan 9, 1962 - [AD 61-24-04](https://openairdocs.org/ad/61-24-04): Horizontal Stabilizer Rear Spar · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more. Effective Dec 14, 1961 - [AD 61-19-03](https://openairdocs.org/ad/61-19-03): Elevator Bolt Inspection · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more. Effective Sep 8, 1961 - [AD 61-14-05](https://openairdocs.org/ad/61-14-05): Landing Gear Doors · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 5 more. Effective Jul 17, 1961 - [AD 54-22-01](https://openairdocs.org/ad/54-22-01): Flexible Hose Replacement · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 7 more - [AD 54-24-02](https://openairdocs.org/ad/54-24-02): Wing Main Beam Web Inspection · Lockheed 1049C-55, 1049D-55 and 1049E-55 - [AD 54-24-03](https://openairdocs.org/ad/54-24-03): Main Landing Gear Actuating Cylinder Assembly · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 8 more - [AD 55-15-06](https://openairdocs.org/ad/55-15-06): Cooling Air System Rework · Lockheed 1049C-55, 1049D-55, 1049E-55 and 6 more - [AD 55-17-01](https://openairdocs.org/ad/55-17-01): Flap Torque Tube Bolts · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 10 more - [AD 55-23-02](https://openairdocs.org/ad/55-23-02): Outer Wing Main Beam Web · Lockheed 1049C-55, 1049D-55, 1049E-55 and 1 more - [AD 55-23-03](https://openairdocs.org/ad/55-23-03): Landing Gear Cylinder Assy. · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 10 more - [AD 56-16-02](https://openairdocs.org/ad/56-16-02): Automatic Pilot Servo Brackets · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more - [AD 56-25-04](https://openairdocs.org/ad/56-25-04): Flap Symmetry · Lockheed 1049-54, 1049C-55, 149-46 and 5 more - [AD 56-26-01](https://openairdocs.org/ad/56-26-01): Main Relay Box Rework · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 5 more - [AD 57-03-02](https://openairdocs.org/ad/57-03-02): Fuel Strainer Screen · Boeing DC-7, DC-7B, DC-7C and 15 more - [AD 57-03-03](https://openairdocs.org/ad/57-03-03): Micronic Filter Cover · Boeing DC-7, DC-7B, DC-7C and 16 more - [AD 58-01-05](https://openairdocs.org/ad/58-01-05): Wing Skin and Stringer Inspection · Lockheed 1049-54, 149-46, 49-46 and 4 more - [AD 58-21-01](https://openairdocs.org/ad/58-21-01): Bulkhead Corrosion Inspection · Lockheed 1049-54, 1049C-55, 1049D-55 and 10 more - [AD 59-03-02](https://openairdocs.org/ad/59-03-02): Landing Gear Downlock Guide · Lockheed 1049-54, 149-46, 49-46 and 4 more - [AD 59-12-02](https://openairdocs.org/ad/59-12-02): Bathtub Fitting · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more - [AD 59-18-04](https://openairdocs.org/ad/59-18-04): Wing Spar Web Reinforcement · Lockheed 1049C-55, 1049D-55, 1049E-55 and 2 more - [AD 59-26-07](https://openairdocs.org/ad/59-26-07): Door Latch Brackets · Lockheed 1049-54, 1049C-55, 649-79 and 3 more - [AD 60-05-02](https://openairdocs.org/ad/60-05-02): Fire Protection · Lockheed 1049C-55, 1049D-55, 1049E-55 and 2 more - [AD 60-08-04](https://openairdocs.org/ad/60-08-04): Rudder Torque Tube · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 6 more - [AD 60-10-04](https://openairdocs.org/ad/60-10-04): Fuselage Aft Pressure Bulkhead · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 12 more - [AD 60-10-06](https://openairdocs.org/ad/60-10-06): Landing Gear Drag Strut · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 5 more - [AD 74-08-09 R2](https://openairdocs.org/ad/74-08-09-R2) (historical): Waste Receptacles · Aero Spacelines 377, 377MG, 377SGT and 268 more. Effective Jul 29, 1996 ## Registered aircraft by registry model (OpenAirDocs) - [Lockheed 1049H-82](https://openairdocs.org/model/lockheed-1049h-82): 1 aircraft (registry code 5262121) - [Lockheed 1049-54](https://openairdocs.org/model/lockheed-1049-54): 0 aircraft (registry code 5262102) - [Lockheed 1049B-55](https://openairdocs.org/model/lockheed-1049b-55): 0 aircraft (registry code 5262104) - [Lockheed 1049C-55](https://openairdocs.org/model/lockheed-1049c-55): 0 aircraft (registry code 5262107) - [Lockheed 1049D-55](https://openairdocs.org/model/lockheed-1049d-55): 0 aircraft (registry code 5262110) - [Lockheed 1049E-55](https://openairdocs.org/model/lockheed-1049e-55): 0 aircraft (registry code 5262114) - [Lockheed 1049F-55](https://openairdocs.org/model/lockheed-1049f-55): 0 aircraft (registry code 5262116) - [Lockheed 1049G-82](https://openairdocs.org/model/lockheed-1049g-82): 0 aircraft (registry code 5262120) ## STCs approved under this data sheet (49) - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA1289WE](https://openairdocs.org/stc/SA1289WE): United Control V-557 cockpit voice recorder system.. Flying Tiger Line Inc - [STC SA1843WE](https://openairdocs.org/stc/SA1843WE): Installation of RCA AVQ-50 weather radar with McMillan 7161X radome and Collins 37P-4 glide slope antenna.. Flying Tiger Line Inc - [STC SA219WE](https://openairdocs.org/stc/SA219WE): Modification of 1049 M.L.G. orifice plate.. Flying Tiger Line Inc - [STC SA4-1167](https://openairdocs.org/stc/SA4-1167): Interior modification.. Flying Tiger Line Inc - [STC SA4-1181](https://openairdocs.org/stc/SA4-1181): Passenger interior configuration.. Flying Tiger Line Inc - [STC SA4-1322](https://openairdocs.org/stc/SA4-1322): Fire proofing of main landing gear doors to comply with Airworthiness Directive 60-05-02.. Flying Tiger Line Inc - [STC SA4-1498](https://openairdocs.org/stc/SA4-1498): Interior modification.. Flying Tiger Line Inc - [STC SA4-948](https://openairdocs.org/stc/SA4-948): Overhead emergency exit hatch between fuselage station 278.4 and 296.8 in top centerline of aircraft.. Flying Tiger Line Inc - [STC SA456WE](https://openairdocs.org/stc/SA456WE): Modification to allow operation at the following weights: takeoff - 142,100 pounds; landing - 114,500 pounds; zero fuel - 109,500 pounds.. Flying Tiger Line Inc - [STC SA635WE](https://openairdocs.org/stc/SA635WE): Single Collins 860E-1 distance measuring equipment system.. Flying Tiger Line Inc - [STC SA717WE](https://openairdocs.org/stc/SA717WE): Single Collins 860E-1 distance measuring equipment system.. Flying Tiger Line Inc - [STC SA901WE](https://openairdocs.org/stc/SA901WE): Emergency exit lighting modification deleting the impact switch.. Flying Tiger Line Inc - [STC SA1413WE](https://openairdocs.org/stc/SA1413WE): Installation of an Edo Model 345 Loran System.. Flying Tiger Line Inc - [STC SA1414WE](https://openairdocs.org/stc/SA1414WE): Installation of a Collins 621A-3 ATC transponder system.. Flying Tiger Line Inc - [STC SA4-896](https://openairdocs.org/stc/SA4-896): Incorporate F.T.L. engineering order no 4517-8 dated 8/10/59 to provide for the use of solid cargo loading in the 1049-H aircraft. Flying Tiger Line Inc - [STC SA629WE](https://openairdocs.org/stc/SA629WE): Installation of a single Collins Model 860E-1.. Flying Tiger Line Inc - [STC SA715WE](https://openairdocs.org/stc/SA715WE): Installation of single Collins Model 860E-1 Distance Measuring Equipment System.. Flying Tiger Line Inc - [STC SA718WE](https://openairdocs.org/stc/SA718WE): Interior installation.. Flying Tiger Line Inc - [STC ST00340WI](https://openairdocs.org/stc/ST00340WI): Approval for operation with the right rear door removed and left rear door open.. SAVE A CONNIE, Inc - [STC ST489SO](https://openairdocs.org/stc/ST489SO): Installation of cargo restraining bulkhead.. Aeronautical Engineers, Inc - [STC SA1362WE](https://openairdocs.org/stc/SA1362WE): Collins 642C-1 cockpit voice recorder system.. Airlift Intl Inc - [STC SA186WE](https://openairdocs.org/stc/SA186WE): Interior modification to 108 passenger configuration.. California Airmotive Corporation - [STC SA188WE](https://openairdocs.org/stc/SA188WE): Catenary cargo restraining net at fuselage station 710 on aircraft converted to cargo configurations.. Lockheed Aircraft Service Co - [STC SA189WE](https://openairdocs.org/stc/SA189WE): Modification of air conditioning system for Class E cargo compartment.. Lockheed Aircraft Service Co - [STC SA200SO](https://openairdocs.org/stc/SA200SO): Cockpit voice recording system.. Eastern Airlines Inc - [STC SA233WE](https://openairdocs.org/stc/SA233WE): Structural reinforcement to wing to permit operation at higher weights.. Lockheed Aircraft Service Co - [STC SA36SO](https://openairdocs.org/stc/SA36SO): Cargo loading door, floor structure, fuselage Reinforcements, cargo tie-down devices, etc.. Anson Robert E & Callaway L C Jr - [STC SA4-1074](https://openairdocs.org/stc/SA4-1074): Seat track and other modifications.. Twentieth Century Aircraft - [STC SA4-1371](https://openairdocs.org/stc/SA4-1371): Passenger interior for 105 occupants.. Dollar Lines Ltd - [STC SA4-1396](https://openairdocs.org/stc/SA4-1396): Structural reinforcements.. Dollar Lines Ltd - [STC SA4-1474](https://openairdocs.org/stc/SA4-1474): Weather radar.. California Airmotive Corporation - [STC SA4-1565](https://openairdocs.org/stc/SA4-1565): Interior arrangement for 111 occupants.. California Airmotive Corporation - [STC SA4-1649](https://openairdocs.org/stc/SA4-1649): Increase in zero fuel weight to108,000 pounds.. Lockheed Aircraft Service Co - [STC SA4-310](https://openairdocs.org/stc/SA4-310): Emergency radio transmitter.. Transocean Airlines - [STC SA4-311](https://openairdocs.org/stc/SA4-311): Interior seating change to provide 98 cabin places.. Transocean Airlines - [STC SA4-312](https://openairdocs.org/stc/SA4-312): Ten man life raft stowage provisions.. Transocean Airlines - [STC SA4-316](https://openairdocs.org/stc/SA4-316): Emergency equipment.. Transocean Airlines - [STC SA4-351](https://openairdocs.org/stc/SA4-351): Modification of airplane including removal of coat closet.. Lockheed Aircraft Service Co - [STC SA4-352](https://openairdocs.org/stc/SA4-352): 101 cabin seats and four crewmember seats.. Transocean Airlines - [STC SA4-377](https://openairdocs.org/stc/SA4-377): 112 and 116 cabin seats and four crewmember seats.. Transocean Airlines - [STC SA546WE](https://openairdocs.org/stc/SA546WE): Modification of crew entrance door window mechanism.. Gamco Precision - [STC SA659WE](https://openairdocs.org/stc/SA659WE): Wing skin change.. California Airmotive Corporation - [STC SA6EA](https://openairdocs.org/stc/SA6EA): Pallets and rollers and guide rails.. Eastern Rotorcraft Corporation - [STC SA755WE](https://openairdocs.org/stc/SA755WE): Three 1,800-gallon KC97 fuselage tanks for carriage of petroleum fuels as cargo.. Lockheed Aircraft Service Co - [STC SA83SO](https://openairdocs.org/stc/SA83SO): Oil separator B-300-1.. Air Carrier Eng Service Inc - [STC SA4-608](https://openairdocs.org/stc/SA4-608): Engine mount core assemblies DE-643-1 on Wright TC18 Series engines.. Dow-Elco Inc - [STC SA4-514](https://openairdocs.org/stc/SA4-514) (historical): Interior modification from LAC 494652 drawing changed by FAA approved, sealed Flying Tiger Line Drawing list No. SA4-514. Flying Tiger Line Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.